(d)
Place switch in OFF position and remove electrical power.
(7)
Service hydraulic reservoirs. Refer to Chapter 12, Hydraulic Fluid Servicing.
WARNING: PERSONNEL STAND CLEAR OF RUDDER AND LEADING EDGE DEVICES.
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3. Removal/Installation Standby Hydraulic Pump Motor
A. Remove Hydraulic Pump Motor
(1)
Open standby pump circuit breakers on P6-11 and P6-12 panel.
(2)
Remove electrical connector (9, Fig. 401).
(3)
Remove pump mounting nuts (4).
(4)
Remove mounting bolts (2) and separate motor from pump.
B. Install Hydraulic Pump Motor
(1)
Remove protective plug from port on accessory mounting flange of pump motor.
(2)
Place motor in mounting position and install mounting bolts (2, Fig. 401).
(3)
Engage splines between motor (l) and pump (5). Install pump mounting nuts (4) and install lockwire.
(4)
Install electrical connector (9).
(5)
Check operation of motor in accordance with paragraph 2.E. step (6).
4. Removal/Installation Standby System Pump
A. To remove and install the standby system pump without removing the motor, follow the procedure given in par. 2. except as follows: Instead of removing mounting bolts (2, Fig. 401), separate pump (5) from motor (1) by removing pump mounting nuts (4).
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29-21-22 Page 404 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. May 01/99
STANDBY HYDRAULIC SYSTEM ELECTRIC MOTOR-DRIVEN PUMP - ADJUSTMENT/TEST
EFFECTIVITY
Task/NYAB Installation
1. Standby Hydraulic Pump Test
A. General
(1)
The following test procedure is performed to operationally check the hydraulic pump and the electrical circuits that provide power to the pump.
(2)
A container will be necessary to catch fluid when disconnecting hydraulic lines. Should any fluid spill, decontaminate (Ref Chapter 12, Cleaning and Washing).
B. Equipment and Materials
(1)
Pressure gage - 0 to 3500 psi
(2)
Suitable container for catching hydraulic fluid
C. Prepare Standby Hydraulic Pump for Test
(1)
Install pressure gage in pressure line between pump and standby modular package.
(2)
Pressurize standby reservoir (Ref 29-09-300 MP).
(3)
Close STBY HYD PUMP NORMAL circuit breaker on P6 panel.
(4)
Close STBY HYD PUMP (ALT) circuit breaker on P6 panel.
(5)
Close STBY RUDDER and STBY PUMP CONT circuit breaker on P6 panel.
(6)
Close AC INDICATION BUS NO. 1 PHASE C circuit breaker on P6 panel.
Feb 20/85 29-21-22 Page 501
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(7) Check that following switches are in OFF position:
(a)
Alt Flap Master Arming Switch
(b)
System A Control Switch
(c)
System B Control Switch
D. Test Standby Hydraulic Pump
(1)
Connect electrical power to airplane and check that power is available on No. 1 and 2 generator buses.
(2)
Place system A flight control switch in STBY RUD position. The standby pump should operate and pressure on gage should indicate 3050 (+ 75) psi.
(3)
Open AC INDICATION BUS NO. 1 PHASE C then STBY HYD PUMP (NORMAL) circuit breakers on P6 panel. Check that pump continues to operate.
(4)
Close STBY HYD PUMP (NORMAL) and AC INDICATION NO. BUS 1 PHASE C circuit breakers on P6 panel and open STBY HYD PUMP (ALT) circuit breaker on P6 panel. Check that pump continues to operatte.
(5)
Place system A flight control switch in OFF position. Check that pump stops.
(6)
Place system B flight control switch in STBY RUD position. Check that pump operates.
(7)
Place System B flight control switch in OFF position and check that pump stops.
(8)
Position ALT FLAP arming switch to ARM. Check that pump operates.
(9)
Position ALT FLAP arming switch to OFF. Check that pump stops.
E. Restore Airplane to Normal Configuration
(1)
Remove electrical power from airplane.
(2)
Remove pressure gage from pressure line.
(3)
Service hydraulic reservoirs (Ref Chapter 12, Hydraulic Fluid Servicing).
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